Abstract: A preload reducing fastener adapted to be fastened into a system in which includes a release system. The fastener may have an integral collar which is adapted to change shape, as in the case of a shape memory alloy. The application of heat to fastener may deform the collar such that the fastener may move axially in the load direction, thus reducing the preload previously held by the fastener. A preload reducing device including a preload reducing fastener may include an outer case adapted to center and capture a preload reducing fastener. The case may center the fastener in a desired location in a preloaded system, and may also capture the fastener after release of the system.

Abstract: A redundant release apparatus having a multi-segment split spool with a central bore adapted to axially restrain a tensioned member. Two tensioned tapes are overlappingly wound around the spool segments thereby preventing radial movement of the spool segments. Overlapping winding design of each of the tapes provide predictable unwinding dynamics upon release. The multiple segments require less radial motion for release of the tensioned member.

Abstract: A release device having a multi-segment split spool with a central bore adapted to axially restrain a tensioned member. A tensioned tape is overlappingly wound around the spool segments thereby preventing radial movement of the spool segments. The overlapping winding allows for a low profile housing for the release device. The multiple segments require less radial motion for release of the tensioned member.

Abstract: A redundant release apparatus having a multi-segment split spool with a central bore adapted to axially restrain a tensioned member. Two tensioned tapes are overlappingly wound around the spool segments thereby preventing radial movement of the spool segments. Overlapping winding design of each of the tapes provide predictable unwinding dynamics upon release. The multiple segments require less radial motion for release of the tensioned member.

Abstract: Split spool release apparatus for retaining and deploying a deployable appendage. Exemplary apparatus comprises a housing which houses a split spool clamping device, a release nut attached to the deployable appendage, a locking mechanism or fuse assembly, and an actuator. The split spool clamping device comprises a plurality of separable sections that secure the release nut and deployable appendage using the restraining wire that is wrapped around them. In one embodiment, the split spool clamping device may comprises a threaded split-nut. The restraining wire is preferably wrapped using variable pretension, having low tension at the fuse end and higher tension at the nut end (load application end). The fuse assembly is coupled to the restraining wire at a location that is distal from the deployable appendage, and is activated by the actuator to release the restraining wire.

Abstract: A support for a deployable reflector for use on a modular satellite antenna assembly is constructed of an elongated boom supported at both ends by a pair of two axis actuators. The boom is attached at its inboard end to the satellite structure in close proximity to the point of attachment of the associated signal feed assembly to minimize the differential thermal stress throughout the antenna assembly.

Abstract: A spacecraft having nested reflectors that are released and deployed during a single release event using one or more dual reflector holddowns. The nested reflectors are held in place prior to release by the holddowns and are released during the single release event. The nested reflectors are secured to the body of the spacecraft by hinges attached to respective reflector backup structures and are releasably secured to the body using the one or more dual reflector holddowns. The reflector backup structures are secured by reflector interface brackets of the respective holddowns. An exemplary holddown has a separable tubular housing that is longitudinally secured together between an end cap and a release device. A threaded shaft 28 extends through the tubular housing, the end cap and the release device. A retraction spring is disposed around the exterior of the housing. The reflector interface brackets are secured to the outer and inner housings that attach the plurality of reflectors to the holddown.

Abstract: A highly reliable release apparatus which is used to stow or release desired devices such as, for example, solar arrays, antenna positioning mechanisms, reflectors, found on satellites, space stations or spacecraft. Deployment of the desired device is prevented or allowed by respectively restraining or releasing a first member under tension. The apparatus comprises a support member having an opening and a first face arranged about the opening. A second member is located within the opening when the first member is in tension and is adapted to be attached to an end of the first member. At least three locking members such as fuse wires are arranged on the first face of said support member for restraining the second member within the opening in order to maintain tension on the first member. The second member is attached to the first member in a manner such that at least two of the fuse wires must be severed before the restraint on the second member is released.

Abstract: Dual-axis hinge assemblies comprising mechanical devices which provide integrated synchronous rotation of a support element, such as a space antenna shaft, attached to a vertical hinge shaft about its own axis while simultaneously pivoting the support shaft about a horizontal hinge shaft having a second axis which extends in a direction perpendicular to the axis of the vertical hinge shaft. The hinge assembly is adapted to be mounted parallel to a side surface of a spacecraft body and restrained by a holddown device, and is biased to cause the space antenna to pivot on the horizontal hinge shaft from restrained position to deployed position and to simultaneously turn on its own axis about a vertical hinge shaft when the restraint is removed, to aim the antenna reflector disk in a predetermined direction.

Abstract: A hybrid solar panel array is mounted on a satellite sidewall for movement between a stowed position proximate the satellite sidewall and a deployed position extending away from the satellite sidewall. The array comprises a yoke pivotally mounted on the satellite sidewall and first and second rigid solar panels, the first panel being pivotally mounted to the yoke, the first and second panels being hinged together. In one embodiment, a plurality of semi-rigid solar panels are pivotally mounted to the first and second rigid solar panels. In another embodiment, a flexible solar panel is attached to the rigid solar panels. Drive mechanisms are operable for moving the array from a stowed position proximate a satellite sidewall to a deployed position extending away from the satellite sidewall. The rigid panels are so moved in a synchronous operation and the semi-rigid and flexible solar panels are so moved in a sequential operation.

Abstract: Deployment hinge apparatus comprises a stationary U-shaped bracket including a flange defining a retention recess. A hinge arm for supporting an operating structure such as a communication antenna reflector is pivotally mounted on the stationary bracket for movement between a stowed position and a deployed position. The hinge arm includes a deployment and latching cam which extends to a projecting nose member. A latch arm is pivotally mounted at one end to the stationary bracket and includes a cam follower at its other end operatively engageable with the cam. A spring biases the cam follower into engagement with the cam and is thereby effective to rotate the hinge arm from the stowed position to the deployed position such that, in the deployed position, the nose member and the cam follower are together snugly received in the retention recess, locking the hinge arm in the deployed position.

Abstract: An infant seat which converts from a car seat into a stroller. The infant seat comprises a chair connected to a wheel frame on which the wheel set is mounted. The wheel set consists of front and rear wheels connected by a linking means. When the wheel frame is in a stowed condition, it supports the chair in either a forward-facing or rearward-facing car seat configuration. The wheel set is stowed behind or below the chair while the car seat is secured to the automobile seat by the automobile safety belts threaded through the wheel frame. To convert the car seat into a stroller, the wheel frame rotates about its pinned connections to the chair to simultaneously deploy the linked front and rear wheels. The chair back reclines with respect to the chair bottom to convert the stroller into a carriage. Modifications of the wheel frame allow the infant seat to be converted into an infant rocker. Accessories such as a sun shade and footrest also extend from the chair.

Abstract: A threadless linear actuator apparatus comprising a sealed actuator unit with a sealed housing for a set of spool-shaped roller bearings. The roller bearing set includes at least one variable pitch loading roller and two fixed pitch rollers arranged in a skewed relationship about a cylindrical drive shaft. A variable moment is applied to the apparatus through a moment applied about an axis which is perpendicular to and intersects the drive shaft axis which, when applied, varies the pitch of the pivotable loading roller.

Abstract: A hinge (5) having a first, relatively stationary yoke (8) and a second, relatively rotating yoke (10). A torquing means (17) fixed with respect to the first yoke (8) transmits torque to the second yoke (10) via a block (18) retained within a cavity (20) of an elongated hinge pin (15) that is aligned along the axis of rotation (z) of the two yokes (8, 10). The torquing means (17) is coupled to the hinge pin (15). The yokes (8, 10) self-align about two orthogonal axes (x, y) that are also orthogonal to the axis of rotation (z). The block (18) is free to pivot within the cavity (20) about the x axis, while the second yoke (10) is free to pivot about the y axis about the hinge pin (15) and block (18).